Accession Number : ADA331972

Title :   Vibration, Stability, and Transient Response of Helicopters with Elastically Tailored Composite Rotor Blades.

Descriptive Note : Final progress rept. Jun 94-31 May 97,

Corporate Author : PENNSYLVANIA STATE UNIV UNIVERSITY PARK

Personal Author(s) : Smith, Edward C.

PDF Url : ADA331972

Report Date : 29 SEP 1997

Pagination or Media Count : 5

Abstract : Aeroelastically tailored composite rotor blades offer significant potential for improved stability, reduced vibration, simplified hub design, and improved handling qualities of rotorcraft. Development of new analytical tools to predict the complex dynamic behavior of these rotor systems is essential to the integration of tailored blade technology into next generation rotorcraft systems. The focus of the present work has been: (1) Advancements in analysis methods for open section composite beams, subject to warping restraint effects, (2) Advancement in cross-sectional modeling of thick-walled composite blade sections, (3) Development and application of an aeroelastic analysis for investigation of composite elastic tailoring for stall alleviation and vibration reduction.

Descriptors :   *AEROELASTICITY, *ROTARY WING AIRCRAFT, *ROTOR BLADES, STABILITY, VIBRATION, REDUCTION, STALLING, HELICOPTERS.

Subject Categories : Helicopters
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE